The International Sun-Earth Explorer (ISEE) scientific satellite to be stationed in 1978 in the vicinity of the sun-earth interior libration point to continuously monitor the space between the sun and the earth, including the distant geomagnetic tail is described. Orbit selection considerations for the ISEE-C are discussed along with stationkeeping requirements and fuel-optimal trajectories. Due to the alignment of the interior libration point with the sun as viewed from the earth, it will be necessary to place the satellite into a 'halo orbit' around the libration point, in order to eliminate solar interference with down-link telemetry. Parametric data for transfer trajectories between an earth parking orbit (altitude about 185 km) and a libration-point orbit are presented. It is shown that the insertion magnitude required for placing a satellite into an acceptable halo orbit is rather modest.


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    Titel :

    Mission design for a halo orbiter of the earth


    Beteiligte:
    Farquhar, R. W. (Autor:in) / Muhonen, D. P. (Autor:in) / Richardson, D. L. (Autor:in)

    Kongress:

    Astrodynamics Conference ; 1976 ; San Diego, CA


    Erscheinungsdatum :

    01.08.1976


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Mission design for a halo orbiter of the earth

    FARQUHAR, R. / MUHONEN, D. / RICHARDSON, D. | AIAA | 1976


    Orbiter mission design problems

    Eckman, P. K. | NTRS | 1965


    Lunar Orbiter mission design.

    CRABILL, N. L. / MAYO, W. L. | AIAA | 1969


    Orbiter mission design problems.

    Eckman, P. K. | NTRS | 1965


    Lunar Orbiter mission design.

    Crabill, N. L. / Mayo, W. L. | NTRS | 1969